EP0847363B1 - Aircraft gas turbine engine with a liquid-air heat exchanger - Google Patents

Aircraft gas turbine engine with a liquid-air heat exchanger Download PDF

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Publication number
EP0847363B1
EP0847363B1 EP96921980A EP96921980A EP0847363B1 EP 0847363 B1 EP0847363 B1 EP 0847363B1 EP 96921980 A EP96921980 A EP 96921980A EP 96921980 A EP96921980 A EP 96921980A EP 0847363 B1 EP0847363 B1 EP 0847363B1
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EP
European Patent Office
Prior art keywords
gas turbine
heat exchanger
aircraft gas
duct
turbine engine
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Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP96921980A
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German (de)
French (fr)
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EP0847363A1 (en
Inventor
Dimitrie Negulescu
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Rolls Royce Deutschland Ltd and Co KG
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BMW Rolls Royce GmbH
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Publication of EP0847363A1 publication Critical patent/EP0847363A1/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/12—Cooling of plants
    • F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
    • B64D33/10—Radiator arrangement
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the invention relates to an aircraft gas turbine engine, in particular a turboprop engine, with a liquid-air heat exchanger arranged in the engine nacelle, especially an oil cooler that is driven by a fed through an opening in the engine nacelle Cooling air flow can be acted upon.
  • a liquid-air heat exchanger arranged in the engine nacelle, especially an oil cooler that is driven by a fed through an opening in the engine nacelle Cooling air flow can be acted upon.
  • Aircraft turbine engines may require air-cooled To arrange liquid heat exchangers and especially oil coolers that these heat exchangers both during flight operations and when rolling forward of the plane, as well as when the plane is on the ground rolls backwards, optimally flowed with cooling air. Of special This requirement is important for turboprop engines because of the oil coolers of these engines dissipate relatively large amounts of heat have to.
  • a problem in particular when the aircraft rolls backwards is the promotion of the air flow acting on the heat exchanger. It is therefore an object of the present invention to provide a particularly premature solution to this problem.
  • the heat exchanger is arranged in a flow channel, which opens at the rear in the environment and which can be optionally connected at the front to an air inlet opening or to the inflow channel of the compressor of the aircraft gas turbine.
  • Advantageous training and further education are included in the subclaims.
  • the invention is explained in more detail with reference to the schematic diagram of a preferred one Embodiment.
  • the engine nacelle of a turboprop engine shown only partially.
  • an aircraft gas turbine arranged, of which essentially only the compressor 2 is shown is.
  • the aircraft gas turbine drives a propeller 4.
  • the lubricating oil of the transmission 3 is heated so much that always a effective oil cooling must take place; this is essentially within the engine nacelle 1 is a liquid-air heat exchanger 5, which follows is also referred to as an oil cooler 5.
  • the engine nacelle 1 On the front side the engine nacelle 1 is provided with an air inlet opening 7 the flow channel 6 can be connected.
  • a flow guide flap designated by 10 in the dashed line Position In this case a flow guide flap designated by 10 in the dashed line Position.
  • the flow channel 6 opens on the other side of the Oil cooler 5 either through a conventional nozzle according to arrow 16 in the area, by moving a movable flap 15, the flow channel 6 but also via an overflow opening 8 in the engine nacelle 1 be connected to the environment.
  • a so-called connecting channel branches from the flow channel 6 near the air inlet opening 7 9, with an adjustable in the area of the junction Flow guide flap 10 is provided.
  • the flow guide flap 10 is pivotable about a pivot point 13. Shown is this flow guide valve 10 in its two different End positions.
  • the flow guide flap 10 is shown in dashed lines shown position, there is a possible connection from the flow channel 6 interrupted to the connecting channel 9, d. H. it is not airborne from Flow channel 6 in the connecting channel 9 possible.
  • connection channel 9 can establish a connection between the Flow channel 6 and the inflow channel 11 of the compressor 2, via which the gas turbine operating air is supplied to the compressor 2.
  • the flow channel is located in the front area of the engine nacelle 1 6 essentially next to the inflow channel 11.
  • the flow guide flap 10 from the position shown in dashed lines to the Position shown by a solid line, so is now over opened connecting channel 9, the flow channel 6 with the inflow channel 11 connected while the air inlet opening 7 is closed becomes.
  • the flap 15 is moved such that the nozzle is closed and the transfer opening 8 is opened. This has the consequence that when operating the gas turbine or the compressor 2 air from the flow channel 6 is suctioned into the inflow duct 11.
  • the partially relatively hot cooler exhaust air should be supplied this application of hot air to the compressor 2 as well as possible distributed evenly over the circumference of the compressor.
  • the inflow channel 11 of the compressor 2 is ring-shaped as usual also the connecting channel 9 of the essentially annular engine nacelle 1 adapted also annular. With the transfer of Radiator exhaust air via the open flow guide flap 10 into the connecting duct 9 this hot radiator exhaust air will at least essentially distribute evenly over this annular connecting channel 9 and thus essentially evenly distributed in the compressor inflow channel 11 arrive.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Supercharger (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Heat-Exchange Devices With Radiators And Conduit Assemblies (AREA)

Description

Die Erfindung betrifft ein Fluggasturbinen-Triebwerk, insbesondere Turboprop-Triebwerk, mit einem in der Triebwerks-Gondel angeordneten Flüssigkeits-Luft-Wärmetauscher, insbesondere Ölkühler, der von einem zwangsgeförderten, über eine Öffnung in der Triebwerks-Gondel zugeführten Kühlluftstrom beaufschlagbar ist. Zum bekannten Stand der Technik wird beispielshalber auf die EP 0 514 119 A1 verwiesen.The invention relates to an aircraft gas turbine engine, in particular a turboprop engine, with a liquid-air heat exchanger arranged in the engine nacelle, especially an oil cooler that is driven by a fed through an opening in the engine nacelle Cooling air flow can be acted upon. The known prior art For example, refer to EP 0 514 119 A1.

An Fluggasturbinen-Triebwerken kann es erforderlich sein, luftgekühlte Flüssigkeits-Wärmetauscher und insbesondere Ölkühler so anzuordnen, daß diese Wärmetauscher sowohl bei Flugbetrieb sowie beim Vorwärts-Dahinrollen des Flugzeuges, als auch dann, wenn das Flugzeug am Boden rückwärts dahinrollt, optimal mit Kühlluft angeströmt werden. Von besonderer Bedeutung ist diese Anforderung bei Turboprop-Triebwerken, da über die Ölkühler dieser Triebwerke relativ große Wärmemengen abgeführt werden müssen.Aircraft turbine engines may require air-cooled To arrange liquid heat exchangers and especially oil coolers that these heat exchangers both during flight operations and when rolling forward of the plane, as well as when the plane is on the ground rolls backwards, optimally flowed with cooling air. Of special This requirement is important for turboprop engines because of the oil coolers of these engines dissipate relatively large amounts of heat have to.

Ein Problem insbesondere beim Rückwärts-Dahinrollen des Flugzeuges ist dabei die Förderung des den Wärmetauscher beaufschlagenden Luftstromes. Eine besonders voreilhafte Lösung für dieses Problem aufzuzeigen, ist demzufolge Aufgabe der vorliegenden Erfindung.
Zur Lösung dieser Aufgabe ist vorgesehen, daß der Wärmetauscher in einem Strömungskanal angeordnet ist, der rückseitig in der Umgebung mündet und der vorderseitig wahlweise mit einer Lufteintrittsöffnung oder mit dem Zuströmkanal des Verdichters der Fluggasturbine verbindbar ist. Vorteilhafte Aus- und Weiterbildungen sind Inhalt der Unteransprüche.A problem in particular when the aircraft rolls backwards is the promotion of the air flow acting on the heat exchanger. It is therefore an object of the present invention to provide a particularly premature solution to this problem.
To solve this problem it is provided that the heat exchanger is arranged in a flow channel, which opens at the rear in the environment and which can be optionally connected at the front to an air inlet opening or to the inflow channel of the compressor of the aircraft gas turbine. Advantageous training and further education are included in the subclaims.

Näher erläutert wird die Erfindung anhand der Prinzipskizze eines bevorzugten Ausführungsbeispieles. Dabei ist mit der Bezugsziffer 1 die Triebwerks-Gondel eines nur teilweise dargestellten Turboprop-Triebwerks bezeichnet. In dieser in einem Teilschnitt dargestellten Triebwerks-Gondel ist eine Fluggasturbine angeordnet, von der im wesentlichen nur der Verdichter 2 dargestellt ist. Unter Zwischenschaltung eines Getriebes 3 treibt die Fluggasturbine einen Propeller 4 an. Aufgrund der hohen zu übertragenden Leistung wird das Schmieröl des Getriebes 3 so stark erwärmt, daß stets eine wirkungsvolle Ölkühlung erfolgen muß; hierzu ist im wesentlichen innerhalb der Triebwerks-Gondel 1 ein Flüssigkeits-Luft-Wärmetauscher 5, der im folgenden auch als Ölkühler 5 bezeichnet wird, angeordnet.The invention is explained in more detail with reference to the schematic diagram of a preferred one Embodiment. With the reference number 1 is the engine nacelle of a turboprop engine shown only partially. In this engine nacelle shown in a partial section is an aircraft gas turbine arranged, of which essentially only the compressor 2 is shown is. With the interposition of a transmission 3, the aircraft gas turbine drives a propeller 4. Because of the high power to be transmitted the lubricating oil of the transmission 3 is heated so much that always a effective oil cooling must take place; this is essentially within the engine nacelle 1 is a liquid-air heat exchanger 5, which follows is also referred to as an oil cooler 5.

Es gilt, diesen Ölkühler 5 stets mit einem Kühlluftstrom zu beaufschlagen. Hierzu ist der Ölkühler/Wärmetauscher 5 in einem Strömungskanal 6, der in die Triebwerks-Gondel 1 eingearbeitet ist, angeordnet. An der Vorderseite der Triebwerks-Gondel 1 ist eine Lufteintrittsöffnung 7 vorgesehen, die mit dem Strömungskanal 6 verbunden werden kann. In diesem Falle befindet sich eine mit 10 bezeichnete Strömungs-Leitklappe in der gestrichelt dargestellten Position. Der Strömungskanal 6 mündet auf der anderen Seite des Ölkühlers 5 entweder über eine übliche Düse gemäß Pfeil 16 in der Umgebung, durch Verschiebung einer beweglichen Klappe 15 kann der Strömungskanal 6 jedoch auch über eine Übertrittsöffnung 8 in der Triebwerks-Gondel 1 mit der Umgebung verbunden sein. It is important to always apply a flow of cooling air to this oil cooler 5. For this purpose, the oil cooler / heat exchanger 5 in a flow channel 6, which in the engine nacelle 1 is incorporated. On the front side the engine nacelle 1 is provided with an air inlet opening 7 the flow channel 6 can be connected. In this case a flow guide flap designated by 10 in the dashed line Position. The flow channel 6 opens on the other side of the Oil cooler 5 either through a conventional nozzle according to arrow 16 in the area, by moving a movable flap 15, the flow channel 6 but also via an overflow opening 8 in the engine nacelle 1 be connected to the environment.

Nahe der Lufteintrittsöffnung 7 zweigt vom Strömungskanal 6 ein sog. Verbindungskanal 9 ab, wobei im Bereich der Abzweigung eine verstellbare Strömungs-Leitklappe 10 vorgesehen ist. Mittels eines Verstellhebels 12 ist die Strömungsleitklappe 10 um einen Drehpunkt 13 verschwenkbar. Dargestellt ist diese Strömungs-Leitklappe 10 in ihren beiden unterschiedlichen Endpositionen. Befindet sich die Strömungs-Leitklappe 10 in der gestrichelt dargestellten Lage, so ist eine mögliche Verbindung vom Strömungskanal 6 zum Verbindungskanal 9 unterbrochen, d. h. es ist kein Luftübertritt vom Strömungskanal 6 in den Verbindungskanal 9 möglich. Über die Lufteintrittsöffnung 7 kann dann der Kühlluftstrom zur Beaufschlagung des Ölkühlers 5 direkt in den Strömungskanal 6 eintreten und stromab des Ölkühlers 5 als Kühler-Abluftstrom gemäß Pfeil 16 über die Düse wieder in die Umgebung austreten; die dargestellte Pfeilrichtung 14 ist in diesem Falle ohne Bedeutung.A so-called connecting channel branches from the flow channel 6 near the air inlet opening 7 9, with an adjustable in the area of the junction Flow guide flap 10 is provided. By means of an adjusting lever 12 the flow guide flap 10 is pivotable about a pivot point 13. Shown is this flow guide valve 10 in its two different End positions. The flow guide flap 10 is shown in dashed lines shown position, there is a possible connection from the flow channel 6 interrupted to the connecting channel 9, d. H. it is not airborne from Flow channel 6 in the connecting channel 9 possible. Via the air inlet opening 7 can then the cooling air flow to act on the oil cooler 5 enter directly into the flow channel 6 and downstream of the oil cooler 5 as cooler exhaust air flow according to arrow 16 via the nozzle back into the environment emerge; the arrow direction 14 shown is without in this case Meaning.

Der Verbindungskanal 9 kann eine Verbindung herstellen zwischen dem Strömungskanal 6 sowie dem Zuströmkanal 11 des Verdichters 2, über welchen dem Verdichter 2 die Gasturbinen-Betriebsluft zugeführt wird. Wie ersichtlich liegt im vorderen Bereich der Triebwerks-Gondel 1 der Strömungskanal 6 im wesentlichen neben dem Zuströmkanal 11. Wird nun die Strömungs-Leitklappe 10 aus der gestrichelt dargestellten Position in die mit durchgezogener Linie dargestellte Position gebracht, so wird über den nunmehr geöffneten Verbindungskanal 9 der Strömungskanal 6 mit dem Zuströmkanal 11 verbunden, während die Lufteintrittsöffnung 7 geschlossen wird. Gleichzeitig wird die Klappe 15 derart verschoben, daß die Düse geschlossen und die Übertrittsöffnung 8 geöffnet wird. Dies hat zur Folge, daß bei Betrieb der Gasturbine bzw. des Verdichters 2 Luft aus dem Strömungskanal 6 in den Zuströmkanal 11 abgesaugt wird. Als Folge hiervon gelangt ein Luftstrom gemäß Pfeilrichtung 14 über die Übertrittsöffnung 8 in den Strömungskanal 6, durchdringt den Ölkühler 5 und wird schließlich vom Verdichter 2 abgesaugt. Diese Betriebsweise bzw. diese Stellung der Strömungs-Leitklappe 10 sowie der verschiebbaren Klappe 15 wird somit dann gewählt, wenn zu Kühlungszwecken durch den Ölkühler 5 ein Luftstrom geschickt werden soll, wenn jedoch - beispielsweise wegen einer Rückwärtsfahrt des Flugzeuges - über die Lufteintrittsöffnung 7 praktisch kein Luftstrom zum Ölkühler 5 gelangen kann. Im Sinne einer vorteilhaften Funktionsvereinigung fungiert der Verdichter 2 dann gleichzeitig als Fördervorrichtung für einen den Flüssigkeits-Luft-Wärmetauscher 5 beaufschlagenden Kühlluftstrom.The connection channel 9 can establish a connection between the Flow channel 6 and the inflow channel 11 of the compressor 2, via which the gas turbine operating air is supplied to the compressor 2. As can be seen the flow channel is located in the front area of the engine nacelle 1 6 essentially next to the inflow channel 11. Now the flow guide flap 10 from the position shown in dashed lines to the Position shown by a solid line, so is now over opened connecting channel 9, the flow channel 6 with the inflow channel 11 connected while the air inlet opening 7 is closed becomes. At the same time, the flap 15 is moved such that the nozzle is closed and the transfer opening 8 is opened. This has the consequence that when operating the gas turbine or the compressor 2 air from the flow channel 6 is suctioned into the inflow duct 11. As a result of this an air flow in the direction of arrow 14 via the transfer opening 8 in the Flow channel 6, penetrates the oil cooler 5 and is finally from Compressor 2 aspirated. This mode of operation or this position of the flow guide flap 10 and the sliding flap 15 will then selected if an air flow is sent through the oil cooler 5 for cooling purposes should, however, if - for example because of a backward drive of the aircraft - practically no air flow via the air inlet opening 7 can get to the oil cooler 5. In the sense of an advantageous combination of functions The compressor 2 then simultaneously functions as a conveying device for a liquid-air heat exchanger 5 acting Cooling air flow.

Da dem Verdichter 2 beim Fördern des den Ölkühler 5 beaufschlagenden Kühlluftstromes die teilweise relativ heiße Kühler-Abluft zugeführt wird, sollte diese Beaufschlagung des Verdichters 2 mit heißer Luft so gut als möglich über den Umfang des Verdichters gleichmäßig verteilt erfolgt. Da der Zuströmkanal 11 des Verdichters 2 wie üblich ringförmig ausgebildet ist, ist ebenfalls der Verbindungskanal 9 der im wesentlichen ringförmigen Triebwerks-Gondel 1 angepaßt ebenfalls ringförmig ausgebildet. Mit Übertritt der Kühler-Abluft über die geöffnete Strömungs-Leitklappe 10 in den Verbindungskanal 9 wird sich diese heiße Kühlerabluft zumindest im wesentlichen gleichmäßig über diesen ringförmigen Verbindungskanal 9 verteilen und somit im wesentlichen gleichmäßig verteilt in den Verdichter-Zuströmkanal 11 gelangen. Wird zum einen späteren Zeitpunkt das beschriebene Fluggasturbinen-Triebwerk wieder von vorne angeströmt, so daß ein ausreichend hoher, die Lufteintrittsöffnung 7 beaufschlagender Kühlluftstrom zur Verfügung steht, so wird die Strömungs-Leitklappe 10 wieder in die in gestrichelter Linie dargestellte Position gebracht, so daß der Ölkühler 5 wieder wie üblich bezüglich des Triebwerkes von vorne nach hinten mit Kühlluft durchströmt wird. Mit der beschriebenen Anordnung ist es somit möglich, unter sämtlichen Betriebszuständen auf einfache Weise einen ausreichend großen Kühlluftstrom für die Beaufschlagung des Flüssigkeits-Luft-Wärmetauschers bzw. Ölkühlers 5 bereitzustellen. Dabei können selbstverständlich eine Vielzahl von Details insbesondere konstruktiver Art durchaus abweichend vom gezeigten Ausführungsbeispiel gestaltet sein, ohne den Inhalt der Patentansprüche zu verlassen.Since the compressor 2 when pumping the oil cooler 5 acting Cooling air flow, the partially relatively hot cooler exhaust air should be supplied this application of hot air to the compressor 2 as well as possible distributed evenly over the circumference of the compressor. Because the inflow channel 11 of the compressor 2 is ring-shaped as usual also the connecting channel 9 of the essentially annular engine nacelle 1 adapted also annular. With the transfer of Radiator exhaust air via the open flow guide flap 10 into the connecting duct 9 this hot radiator exhaust air will at least essentially distribute evenly over this annular connecting channel 9 and thus essentially evenly distributed in the compressor inflow channel 11 arrive. Will the aircraft gas turbine engine described later flowed again from the front, so that a sufficient high cooling air flow acting on the air inlet opening 7 for Is available, the flow guide valve 10 is again in dashed lines Position shown line, so that the oil cooler 5 again as usual with regard to the engine from the front to the rear with cooling air is flowed through. With the arrangement described it is thus possible sufficient under all operating conditions in a simple manner large cooling air flow for the loading of the liquid-air heat exchanger or to provide oil cooler 5. You can of course a variety of details, particularly of a constructive nature, are quite different be designed from the embodiment shown, without the content leave the claims.

Claims (4)

  1. An aircraft gas turbine engine, especially a turbo-prop engine, with a fluid-air heat exchanger (5) arranged in the engine nacelle (1), which can be subjected to a forced air stream, taken via an opening in the engine nacelle (1),
    characterised in that the heat exchanger (5) is arranged in an air stream duct (6), which opens into the environment at the rear and which can be connected optionally at the front end with an air entry opening (7), or with the infeed duct (11) of the compressor (2) of the aircraft gas turbine.
  2. An aircraft gas turbine engine according to Claim 1,
    characterised in that in the front end region of the engine nacelle (1) a connecting duct (9) having an adjustable air flow guide flap (10) is provided between the compressor infeed duct (11) and the adjacent heat exchanger air stream duct (6).
  3. An aircraft gas turbine engine according to Claim 1 or Claim 2,
    characterised in that the connecting duct (9) of the essentially annular engine nacelle (1) is formed in a matching ring shape.
  4. An aircraft gas turbine engine according to one of the preceding Claims,
    characterised in that the heat exchanger air stream duct (6) opens optionally via a nozzle (arrow 16) or via an overflow opening (8) into the environment.
EP96921980A 1995-07-07 1996-06-13 Aircraft gas turbine engine with a liquid-air heat exchanger Expired - Lifetime EP0847363B1 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
DE19524733A DE19524733A1 (en) 1995-07-07 1995-07-07 Aircraft gas turbine engine with a liquid-air heat exchanger
DE19524733 1995-07-07
PCT/EP1996/002553 WO1997002984A1 (en) 1995-07-07 1996-06-13 Aircraft gas turbine engine with a liquid-air heat exchanger

Publications (2)

Publication Number Publication Date
EP0847363A1 EP0847363A1 (en) 1998-06-17
EP0847363B1 true EP0847363B1 (en) 1999-08-04

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Application Number Title Priority Date Filing Date
EP96921980A Expired - Lifetime EP0847363B1 (en) 1995-07-07 1996-06-13 Aircraft gas turbine engine with a liquid-air heat exchanger

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US (1) US6000210A (en)
EP (1) EP0847363B1 (en)
DE (2) DE19524733A1 (en)
WO (1) WO1997002984A1 (en)

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EP0847363A1 (en) 1998-06-17
WO1997002984A1 (en) 1997-01-30
US6000210A (en) 1999-12-14
DE59602649D1 (en) 1999-09-09
DE19524733A1 (en) 1997-01-09

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